https://scholars.lib.ntu.edu.tw/handle/123456789/576173
Title: | Performance enhancement of an ethylene-fueled scramjet combustor using a porous cylindrical burner | Authors: | Lee W.-S Pan K.-L. KUO-LONG PAN |
Keywords: | Aliphatic compounds; Combustors; Computational fluid dynamics; Ethylene; Flow of fluids; Open source software; Open systems; Propulsion; Ramjet engines; Struts; Supersonic aerodynamics; Turbulence models; Flame stabilization; Flow-shielding effects; Fuel mass flow rates; Performance enhancements; Porous cylindrical burner; Scramjet combustion chamber; Thermal interaction; Three dimensional flow field; Combustion | Issue Date: | 2019 | Source: | AIAA Propulsion and Energy Forum and Exposition, 2019 | Abstract: | Three-dimensional flow field in a scramjet combustion chamber has been investigated numerically using an open source CFD software OpenFOAM. The LES turbulence model and PaSR combustion model are implemented. Several validations have been performed against published literature to ensure the numerical settings and accuracy. By adding a porous cylindrical burner downstream of the strut injector, the ignition and flame holding problem of an ethylene-fueled DLR combustor can be overcome, as compared to the original configuration. Several significant factors such as net thrust, momentum and pressure transformation, flame extinction, and flame stabilization mechanism have been studied. Taking the advantage of flow control and thermal interaction, the goal of drag reduction and flame holding can both be achieved when the porous cylindrical burner is added in the wake region of the strut at L/D = 1.7. The bow shock could be suppressed due to flow shielding effect provided by upstream strut. As a consequence, higher net thrust and specific impulse at the same fuel mass flow rate can be obtained as compared to the original configuration. Furthermore, larger fuel penetration depth, larger flame spreading area and higher oxygen consumption ratio can be obtained, leading to more suitable condition for a nozzle to produce thrust. ? 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. |
URI: | https://www.scopus.com/inward/record.uri?eid=2-s2.0-85095969134&doi=10.2514%2f6.2019-4232&partnerID=40&md5=a4e7884a3af4133e9b7f8664afc27064 https://scholars.lib.ntu.edu.tw/handle/123456789/576173 |
DOI: | 10.2514/6.2019-4232 |
Appears in Collections: | 機械工程學系 |
Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.